CN116522546B - Container configuration reverse solving method for uniformly removing blade part through barreling finishing - Google Patents
Container configuration reverse solving method for uniformly removing blade part through barreling finishing Download PDFInfo
- Publication number
- CN116522546B CN116522546B CN202310807478.4A CN202310807478A CN116522546B CN 116522546 B CN116522546 B CN 116522546B CN 202310807478 A CN202310807478 A CN 202310807478A CN 116522546 B CN116522546 B CN 116522546B
- Authority
- CN
- China
- Prior art keywords
- blade
- container
- configuration
- normal force
- uniformity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 76
- 238000009826 distribution Methods 0.000 claims abstract description 32
- 238000011077 uniformity evaluation Methods 0.000 claims abstract description 23
- 238000012545 processing Methods 0.000 claims abstract description 22
- 238000004088 simulation Methods 0.000 claims abstract description 16
- 239000013598 vector Substances 0.000 claims description 47
- 239000002245 particle Substances 0.000 claims description 27
- 230000008569 process Effects 0.000 claims description 22
- 230000008859 change Effects 0.000 claims description 13
- 239000011159 matrix material Substances 0.000 claims description 11
- 238000007730 finishing process Methods 0.000 claims description 10
- 238000011156 evaluation Methods 0.000 claims description 6
- 238000004364 calculation method Methods 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 3
- 239000002356 single layer Substances 0.000 claims description 3
- 239000012798 spherical particle Substances 0.000 claims description 2
- 238000007517 polishing process Methods 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 238000005457 optimization Methods 0.000 abstract description 2
- 238000009827 uniform distribution Methods 0.000 abstract 1
- 238000005498 polishing Methods 0.000 description 12
- 230000003746 surface roughness Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 230000007547 defect Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000013519 translation Methods 0.000 description 2
- 238000007514 turning Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006748 scratching Methods 0.000 description 1
- 230000002393 scratching effect Effects 0.000 description 1
- 238000000638 solvent extraction Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000010408 sweeping Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/25—Design optimisation, verification or simulation using particle-based methods
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Evolutionary Computation (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
Abstract
The invention belongs to the technical field of finishing processing of blade parts, and solves the problems that the surface processing of a blade basin and a blade back of the blade part is uneven, the surface processing is nearly over-polished at an exhaust edge, the surface accuracy is difficult to guarantee, and the like. The method comprises the steps of providing a container configuration reverse method for uniformly removing the barreled part through barreling finishing processing, and constructing a blade surface uniformity evaluation model; obtaining the distribution characteristics of normal forces applied to different positions of the blade surface based on simulation and experimental results; the normal force distribution of each position of the blade based on wall effect feedback is obtained by changing the local structure of the container, and the discrete points of each position of the container are reversely calculated by the arrangement and combination and the optimization of the blade surface uniformity evaluation model; and connecting the discrete points into a smooth closed curve by adopting a B spline curve, and reversely solving a container boundary based on the uniform distribution of the normal force of the blade surface. The invention can realize the uniform removal of the blade surface material on the premise of not damaging the precision of the blade profile, and comprehensively improves the uniformity and the surface integrity of thin-wall parts.
Description
Technical Field
The invention belongs to the technical field of blade part finishing processing, and particularly relates to a container configuration reverse solving method for uniformly removing blade part by barreling finishing processing.
Background
The blade is used as a core component with the greatest energy conversion and quantity in an aeroengine, and works in extremely severe environments of centrifugal load, thermal stress and corrosion for a long time, and the manufacturing quality directly influences the service performance and service life of the engine. After the blade is formed by precision forging or precision casting, the surface roughness Ra of the blade is still larger, and the partial area has the defects of high points and the like, so that the surface roughness Ra is required to be reduced to below 0.4 mu m by various polishing and grinding technologies on the premise of not damaging the profile precision of the blade. Because the blade parts have the characteristics of any overlapped space curved surface such as bending, twisting and sweeping, weak rigidity, difficult fixation and the like, the problems of poor accessibility, low polishing efficiency, poor processing uniformity, easy over polishing of front and rear edges and the like exist in the conventional various polishing and grinding processes when the blades are processed.
At present, tools such as abrasive belts, felt wheels and the like are mainly adopted for manual polishing in enterprises, and the defects of high randomness of manual positioning, difficult control of polishing force, difficult guarantee of blade profile precision, high harm to the body health of operators and the like exist. When the traditional centrifugal, rotational flow and vertical vibration type processes are used for processing free-form surface parts, workpieces are freely placed in a container, so that the defects of uneven processing of a material facing surface and a material backing surface, over-polishing of a near exhaust edge, difficulty in ensuring the profile precision and the like are easily caused, and therefore, high-performance parts such as aero-engine blades and the like are difficult to process.
Disclosure of Invention
The invention aims to solve at least one technical problem in the prior art, and provides a container configuration reverse method for uniformly removing the barreling finishing processing of blade parts, wherein the blades are fixed in a container to construct a container structure suitable for the structural characteristics of the blades, and under the action of a wall effect, the normal force distribution characteristics of particles acting on each position of the surface of the blades are uniform, so that the surface roughness of the blades is reduced on the premise of not damaging the original dimensional accuracy of the blades, the surface integrity of the blades is comprehensively improved, and a theoretical method is provided for uniformly removing the complex curved surface parts in the barreling finishing processing.
The invention is realized by adopting the following technical scheme: a container configuration reverse method for uniformly removing in the barreling finishing processing of blade parts comprises the following steps:
s1: constructing a blade surface uniformity evaluation model based on normal force equal distribution;
s2: based on structural characteristics of the blade, dividing the blade into data blocks along the chord length direction and the blade body length direction by taking single particle size as interval, wherein the data blocks are distributed along the chord length directionGroup, distribute +.>Grouping and constructing an initial configuration of the container;
s3: dividing the machining process into steps according to the movement characteristics of the bladeThe number of partial configurations of the containers per stage is variable +.>The method comprises the steps of representing discrete element simulation on containers under different local configurations to obtain the distribution characteristics of normal force born by each position of the blades with different local configurations at different stages;
s4, calculating optimal combinations of local configurations in different rotation stages by adopting an array combination method according to simulation results and using a blade surface uniformity evaluation model, and obtaining container boundary discrete point coordinates corresponding to the local configurations based on the optimal combinations;
s5: adopting B spline curve fitting to solve discrete point coordinates of different stages to form a container section curve based on the B spline curve;
s6: and (3) lofting the section curve of the container along the length direction of the container to obtain a final container configuration, performing discrete element simulation to verify, and if the uniformity requirement is not met, returning to the step (S2) and repeating the steps (S2-S6) until the uniformity requirement of the blade is met, so as to obtain the final container configuration.
Preferably, in step S3, the initial position of the fixed blade in the container is unchanged, the distance between the wall of the container and the blade in different stages is changed, and discrete element simulation is performed on the barreling finishing process of the blade parts.
Preferably, the single change in the distance of the vessel wall from the vane is the thickness of a monolayer of particles.
Preferably, at some stage of the blade processing, the container part structure is changed inwardly or outwardly from the original configuration by an amount ofAt the time, by +.>As a numerical range of the normal force extracted in each data block of the blade surface, it is expressed as +.>Dividing into +.>And counting the frequency in each interval section to obtain the normal force distribution of the particle swarm acting on the surface of the blade in a certain period of time in each data block, wherein the normal force distribution is expressed as follows in a vector form:
in the method, in the process of the invention,the amount of change in the container part-structure to the inside or to the outside in comparison with the initial configuration is +.>Time->Vector expression of normal force distribution in each data block; />Is->The frequency of the normal force of the first interval within a data block, and so on.
Preferably, the method comprises the steps of,is the size of single particles; if the shape of the particles is spherical, the corresponding +.>Is the diameter of the spherical particles; if the shape of the particles is prismatic, the corresponding +.>The edge length of the prismatic particles; if the shape of the particles is conical, corresponding +.>Is the diameter of the bottom surface of the conical particles.
Preferably, in step S4, when the gyration motion isStage, the number of partial configurations of the corresponding container is +.>When in use, the two parts are arranged and combined to coexist at +.>Individual combinations, expression of permutation combination matrix +.>The method comprises the following steps:
wherein each behavior of the matrix is expressed by vectors under different local configurations of the container at the stage, and the first behavior is expressed by corresponding vectors under the initial configuration of the container;the amount of change in the partial structure of the container is either inward or outward from the initial configuration,for data blocksIs the number of (3);
when constructing the blade surface uniformity evaluation model, the contrast vector of normal force vectors in all data blocks on the blade surface needs to be constructedThe expression is as follows:
the expression of the blade surface uniformity evaluation model is:
in the method, in the process of the invention,to evaluate the difference coefficient of the blade surface uniformity, +.>For the difference of the modes>The angular difference for each vector;
wherein the difference of the modesThe expression of (2) is:
angular difference of each vectorThe expression of (2) is:
in the method, in the process of the invention,is the +.>Each interval;
by the difference coefficient of the uniformity of the surface of the bladeAnd calculating the optimal combination of the stage for the evaluation index to obtain the discrete point coordinates of the container boundary under the optimal combination.
Preferably, in step S4, when the uniformity of the distribution of the normal force of the blade along the chord length direction is poor in the processing process of the blade and the container, the data blocks of the blade surface along the length direction of the blade body are integrated into a group, so that the uniformity of the blade surface in one direction is improved;
when the rotary motion isStage, the number of partial configurations of the corresponding container is +.>When the two are arranged and combined, the two are coexistentIndividual combinations, expression of permutation combination matrix +.>The method comprises the following steps:
the equivalent vector calculation formula for the single set of vectors is as follows:
wherein:is a containerThe local structure has an inward or outward variation of +.>When the blade surface is in the chord length direction +.>Equivalent vectors of the group vectors; />The number of data blocks along the length direction of the blade body;
the expression of the blade surface uniformity evaluation model is:
in the method, in the process of the invention,to evaluate the difference coefficient of the blade surface uniformity, +.>For the difference of the modes>The angular difference for each vector;
wherein the difference of the modesThe expression of (2) is:
angular difference of each vectorThe expression of (2) is:
in the method, in the process of the invention,is the +.>Each interval;
by the difference coefficient of the uniformity of the surface of the bladeAnd calculating the optimal combination of the stage for the evaluation index to obtain the discrete point coordinates of the container boundary under the optimal combination.
Preferably, the optimal combination of a certain stage is calculated, and the combination matrix is arrangedEach row of the blade surface uniformity evaluation model is selected to form a vector set, and the vector set is substituted into an expression of the blade surface uniformity evaluation model to obtain corresponding +.>A value; finally choose->The smallest group is used as the optimal permutation and combination; and taking the midpoint set of the container boundary corresponding to the obtained optimal combination as the discrete point coordinates of the container boundary at the stage.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides an evaluation index of equal distribution of normal force applied to each position of the blade surface, and constructs a blade surface uniformity evaluation model; obtaining the distribution characteristics of normal forces applied to different positions of the blade surface based on simulation and experimental results and forming formula expression; the normal force distribution of each position of the blade based on wall effect feedback is obtained by changing the local structure of the container, and the discrete points of each position of the container are reversely calculated by the arrangement and combination and the optimization of the blade surface uniformity evaluation model; connecting a plurality of discrete points into a smooth closed curve by adopting a B spline curve, and reversely solving a container boundary which is uniformly distributed on the basis of normal force of the surface of the blade; the method is based on that the normal force distribution characteristics of particle swarm acting on each position of the blade surface are uniform, the uniform removal of the blade surface material is realized on the premise of not damaging the precision of the blade profile, the surface roughness of the blade is reduced to below 0.4 mu m, and the integrity of the blade surface is comprehensively improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a block diagram of a container configuration inversion method;
FIG. 2 is a schematic diagram of a principle of a barrel finishing process for blade-like parts;
FIG. 3 is a diagram of the normal force raw signal within a block of data;
FIG. 4 is a graph of normal force interval distribution within a block of data;
FIG. 5 is a schematic diagram of a blade surface data block distribution;
fig. 6 is a schematic diagram of the revolution motion phase division;
FIG. 7 is a schematic illustration of the relative positions of the blades installed in the container;
FIG. 8 is a plot of the inverse of the container configuration at 30 degrees of rotation;
FIG. 9 is a schematic illustration of the results of the vessel cross-sectional configuration inversion;
FIG. 10 is a schematic view of the blade, rail and container assembly.
In the figure: 1-a horizontal sliding table; 2-leaf blades; 3-a container; 3.1-left end cap; 3.2-right end cap; 4.1-a main shaft; 4.2-sleeve; 4.3-a container support plate; 4.4-coupling; 4.5-motors; 4.6-spindle support; 4.7-motor support; 4.8-bearings; 5-data blocks; 6-gear bar.
Detailed Description
Technical solutions in the embodiments of the present invention will be clearly and completely described with reference to the drawings in the embodiments of the present invention, and it is apparent that the described embodiments are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the examples of this invention without making any inventive effort, are intended to fall within the scope of this invention.
It should be understood that the structures, proportions, sizes, etc. shown in the drawings are merely for the purpose of understanding and reading the disclosure, and are not intended to limit the scope of the invention, which is defined by the appended claims, and any structural modifications, proportional changes, or dimensional adjustments, which may be made by those skilled in the art, should fall within the scope of the present disclosure without affecting the efficacy or the achievement of the present invention, and it should be noted that, in the present disclosure, relational terms such as first and second are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual relationship or order between such entities.
The present invention provides an embodiment:
as shown in FIG. 1, the method for reversing the configuration of the container uniformly removed by the barreling finishing processing of the blade parts comprises the following steps:
s1: constructing a blade surface uniformity evaluation model based on normal force equal distribution;
s2: based on structural characteristics of the blade, dividing the blade into data blocks along the chord length direction and the blade body length direction by taking single particle size as interval, wherein the data blocks are distributed along the chord length directionGroup, distribute +.>Grouping and constructing an initial configuration of the container;
s3: dividing the machining process into steps according to the movement characteristics of the bladeThe number of partial configurations of the containers per stage is variable +.>The method comprises the steps of representing discrete element simulation on containers under different local configurations to obtain the distribution characteristics of normal force born by each position of the blades with different local configurations at different stages;
s4, calculating optimal combinations of local configurations in different rotation stages by adopting an array combination method according to simulation results and using a blade surface uniformity evaluation model, and obtaining container boundary discrete point coordinates corresponding to the local configurations based on the optimal combinations;
s5: adopting B spline curve fitting to solve discrete point coordinates of different stages to form a container section curve based on the B spline curve;
s6: and (3) lofting the section curve of the container along the length direction of the container to obtain a final container configuration, performing discrete element simulation to verify, and if the uniformity requirement is not met, returning to the step (S2) and repeating the steps (S2-S6) until the uniformity requirement of the blade is met, so as to obtain the final container configuration.
As shown in fig. 2, the method adopted in the barreling and polishing processing of the blade parts in this embodiment is rotary auxiliary horizontal forced vibration and polishing processing: the polishing device comprises a turning device, an electromagnetic vibration system and a horizontal sliding table 1, wherein the turning device is fixed at the horizontal sliding table 1 and driven by the electromagnetic vibration system to realize horizontal sinusoidal movement, and the electromagnetic vibration system is in the prior art and is not described in detail; the blades 2 and the container 3 revolve under the drive of the revolving device; under the combination of revolution motion and horizontal motion, the blades 2 and the container 3 realize rotation auxiliary horizontal forced vibration motion. The micro-actions of collision, rolling, scratching and the like of the particle swarm on the blade 2 can further realize the finishing processing of the blade surface.
The slewing device comprises a main shaft 4.1, a sleeve 4.2, a container supporting plate 4.3, a coupler 4.4, a motor 4.5, a main shaft bracket 4.6 and a motor bracket 4.7; the blades 2 are fixed in the container 3 to form a combined closed cavity, the cavity is fixed on the main shaft 4.1 through the container supporting plate 4.3, and the main shaft 4.1 is connected with the motor 4.5 through the coupling 4.4; the sleeve 4.2 is movably sleeved on the main shaft 4.1 and used for limiting the container supporting plate 4.3, the main shaft 4.1 is rotatably connected to the main shaft bracket 4.6 through a bearing 4.8, and a left end cover 3.1 and a right end cover 3.2 are arranged on two sides of the container 3.
Vector expression of blade surface normal force distribution:
at some stage of the blade processing, the container part structure changes inwards or outwards from the original configuration by an amount ofAt the time, by +.>As a numerical range of the normal force extracted in each data block of the blade surface, it is expressed as +.>Dividing into +.>And counting the frequency in each interval section to obtain the normal force distribution of the particle swarm acting on the surface of the blade in a certain period of time in each data block, wherein the normal force distribution is expressed as follows in a vector form:
in the method, in the process of the invention,the amount of change in the container part-structure to the inside or to the outside in comparison with the initial configuration is +.>Time->Vector expression of normal force distribution in each data block; />Is->The frequency of the normal force of the first interval within a data block, and so on.
Since the average normal force of the workpiece surface is difficult to reflect the real situation that the particle swarm acts on the workpiece surface, the original signal of the normal force in each data block is extracted, as shown in fig. 3; in the embodiment, dividing the normal force into 40 parts by taking 0.005N as an interval from 0 to 0.2N to obtain a normal force distribution histogram of particles acting on the surface of a workpiece in a certain period of time of a single data block, as shown in fig. 4; and expressing the normal force characteristics of the single data block as vectors:
partitioning of blade surface data blocks:
the distribution of the data blocks on the surface of the blade is shown in FIG. 5, the medium selected in the discrete element simulation is a 4mm×4mm inclined triangle grinding block, and the size of a single data block is 4mm×3.8mm; and 8 groups of the blades are uniformly distributed along the length direction of the blade body, 4 groups of the blades are uniformly distributed along the chord length direction of the blade, 32 data blocks are obtained, and normal force distribution in all the data blocks is expressed according to vector calculation of the normal force.
Dividing the revolving motion stage:
the revolution motion is divided into 12 stages in intervals of 30 DEG, the stages are shown in fig. 6, the relative positions of the blades fixed in the container are shown in fig. 7, and the container is shown in fig. 7Indicating gravity (F)>Indicating the length of the container>Representing the width of the container>Representing the height of the container。
The relative position of the fixed blade in the container is unchanged, the distance between the wall of the container and the blade in different stages is changed, discrete element simulation is carried out on the rotary auxiliary horizontal vibration polishing and grinding blade process, and when the angle is 30 degrees, the change amount of the wall distance of the container is 5, and the change amount is +8, +4, 0, -4 and-8 respectively. Wherein 0 indicates no modification on the initial configuration of the container, +4 indicates a 4mm inward translation of the container local boundary, -4 indicates a 4mm outward translation of the container local boundary, and so on. In this embodiment, the container partial structure translates a distance that is the thickness of a monolayer of particles. During the 30 ° rotation phase, when the vessel wall is changed to 0 as compared to the initial configuration, the normal force distribution extracted by each data block on the blade surface is vector expressed as follows:
solving discrete points:
method 1: the uniformity of the blade is improved along the length direction and the chord direction of the blade: in step S4, when the rotary motion isStage, the number of partial configurations of the corresponding container is +.>When the two are arranged and combined, the two are coexistentIndividual combinations, expression of permutation combination matrix +.>The method comprises the following steps:
wherein each behavior of the matrix is expressed by vectors under different local configurations of the container at the stage, and the first behavior is expressed by corresponding vectors under the initial configuration of the container;the amount of change in the partial structure of the container is either inward or outward from the initial configuration,is the number of data blocks;
when constructing the blade surface uniformity evaluation model, the contrast vector of normal force vectors in all data blocks on the blade surface needs to be constructedThe expression is as follows:
the expression of the blade surface uniformity evaluation model is:
in the method, in the process of the invention,to evaluate the difference coefficient of the blade surface uniformity, +.>For the difference of the modes>The angular difference for each vector;
wherein the difference of the modesThe expression of (2) is:
angular difference of each vectorThe expression of (2) is:
in the method, in the process of the invention,is the +.>Each interval;
by the difference coefficient of the uniformity of the surface of the bladeCalculating the optimal combination of the stage for the evaluation index to obtain the container boundary under the optimal combinationDiscrete point coordinates.
Method 2: in the rotation process of the blade and the container, the distribution uniformity of the normal force of the blade along the chord length direction is poor, so that the data blocks of the blade along the length direction of the blade body are integrated into a group, the uniformity of the surface of the blade in one direction is improved, the method is specifically described in the implementation, and the solving process of the method 1 is similar to the method and is not repeated.
The solution of the equivalence vector is as follows:
in the method, in the process of the invention,、/>、/>and->The normal force vectors in the 1 st, 2 nd, 3 rd and 4 th data blocks after integration are compared with each other under the initial configuration respectively; equivalent vector solutions at other stages are similar to this and are not described in detail.
When the rotation stage is 30 DEG (the rotation range is 15 DEG-45 DEG) and the container wall distance is 5, the arrangement and the combination are sharedThe matrix of permutation and combination is as follows:
all the above permutation and combination calculation are carried out by adopting a blade surface uniformity evaluation modelValue and take->The minimum value of the values is 0.7545, and the optimal permutation and combination is (/ -for)>、/>、/>、/>) At this time, the configuration of the container at 30 ° in the rotation stage of the container was reversely found as shown in fig. 8. Establishing a rectangular coordinate system by taking the center of a blade as an origin, taking the length direction of the simplified blade in FIG. 8 as an X axis, taking the connecting line of the midpoint of the simplified blade and the center of a revolution circle as a Y axis, taking the dotted line circle in FIG. 8 as the revolution circle, taking the center point of the boundary of a container corresponding to different data blocks as the required discrete point, and performing parallelogram to obtain 4 discrete point results (10.15, -27.97), (18.15, -34.9), (22.15, -34.9), (26.15, -34.9); the thick solid line portion on the container 3 in fig. 8 is the boundary of the container when the rotation stage is 30 °, and four points of the thick solid line portion are the positions of the corresponding 4 discrete points; in fig. 8, the 5 solid lines of the region where the thick solid line portion is located on the container 3 are sequentially changed by-8, -4, 0, +4, +8, respectively, at positions distant from the center of the revolution circle.
Based on the above method, the container structure in the other 0 ° (rotation range of 0 ° -15 °), 60 ° (rotation range of 45 ° -75 °), 90 ° (rotation range of 75 ° -90 °) rotation stage is reversed, and discrete point results (2, -36.3), (6, -36.3), (23.7, -17.15), (34.63, -21.15), (38.63, -21.15), (46.1, -23.15), (66.3, -6), (66.3, -2) are obtained.
And adopting a B spline curve to carry out fitting solution on discrete points in the rotation stages of 0 degree, 30 degree, 60 degree and 90 degree, and obtaining the final cross-section boundary of the container by taking the origin as the center symmetry.
The formula for the B-spline curve fitting is as follows:
wherein:called->Step->sub-B spline basis function, < >>Is the number of times of painting; wherein-> Is thatIs 2 to the number of control points->Any integer between>Referred to as nodes.
Because the bending degree of the blade is small, the final container boundary can be obtained only by obtaining the container boundary of the container in the stage of 0-90 degrees, and taking the midpoint of the blade as the center to be symmetrical left and right, vertically symmetrical and centrosymmetrically; the coordinates of other discrete points finally obtained are as follows:
finally, the discrete point coordinates of the rotation stages of other 0 DEG (rotation range of-15 DEG to 0 DEG), 330 DEG (rotation range of 315 DEG to 345 DEG), 300 DEG (rotation range of 285 DEG to 315 DEG), 270 DEG (rotation range of 255 DEG to 285 DEG), 240 DEG (rotation range of 225 DEG to 255 DEG), 210 DEG (rotation range of 195 DEG to 225 DEG), 180 DEG (rotation range of 165 DEG to 195 DEG), 150 DEG (rotation range of 135 DEG to 165 DEG), 120 DEG (rotation range of 105 DEG to 135 DEG) and 90 DEG (rotation range of 90 DEG to 105 DEG) are (-2), -36.3), -6, -36.3), -10.15, -27.97), -18.15, -34.9), -22.15, -34.9), -26.15, -34.9), -23.7, -17.15), -34.63, -21.15), -38.63, -21.15), -46.1, -23.15), -66.3, -6), -66.3, -2), -66.3,2), -66.3,6, -46.1,23.15, -38.63,21.15, -34.63,21.15, -23.7,17.15), -26.15, -34.9, -22.15, 34.9, -18.15, -34.9, -10.15,27.97, -6,36.3, -2,36.3, and-2,36.3 (2,36.3), (6,36.3), (10.15,27.97), (18.15, 34.9), (22.15, 34.9), (26.15, 34.9), (23.7,17.15), (34.63,21.15), (38.63,21.15), (46.1,23.15), (66.3,6), (66.3,2) as shown in fig. 9.
And lofting the reversely solved container section boundary along the container length direction curve to obtain a closed container structure. After the container configuration is adopted to carry out rotation auxiliary horizontal vibration simulation on the blades, the uniformity of the abrasion depth of the surfaces of the blades is improved to 0.2510 from the initial 0.3632, and the uniformity is improved by 31%.
A rib 6 is added to the near-exhaust edge and the front end of the tip region of the blade 2 to prevent the particle swarm from over-polishing the blade 2, and the assembly relationship of the blade 2, the rib 6 and the container 3 is shown in fig. 10. An experimental device is built, the surface roughness of the processed blade 2 is reduced to 0.19 mu m from 0.65 mu m, the standard deviation of the surface roughness is reduced to about 0.0201 from 0.0459, the uniformity is improved by 56%, and the effectiveness of the reverse method is proved.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the technical scope of the present invention should be included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A container configuration reverse method for uniformly removing in the barreling finishing processing of blade parts is characterized by comprising the following steps:
s1: constructing a blade surface uniformity evaluation model based on normal force equal distribution;
s2: based on structural characteristics of the blade, dividing the blade into data blocks along the chord length direction and the blade body length direction by taking single particle size as interval, wherein the data blocks are distributed along the chord length directionGroup, distribute +.>Grouping and constructing an initial configuration of the container;
s3: dividing the machining process into steps according to the movement characteristics of the bladeThe number of partial configurations of the containers per stage is variable +.>The method comprises the steps of representing discrete element simulation on containers under different local configurations to obtain the distribution characteristics of normal force born by each position of the blades with different local configurations at different stages;
s4, calculating optimal combinations of local configurations in different rotation stages by adopting an array combination method according to simulation results and using a blade surface uniformity evaluation model, and obtaining container boundary discrete point coordinates corresponding to the local configurations based on the optimal combinations;
s5: adopting B spline curve fitting to solve discrete point coordinates of different stages to form a container section curve based on the B spline curve;
s6: and (3) lofting the section curve of the container along the length direction of the container to obtain a final container configuration, performing discrete element simulation to verify, and if the uniformity requirement is not met, returning to the step (S2) and repeating the steps (S2-S6) until the uniformity requirement of the blade is met, so as to obtain the final container configuration.
2. The method for reversing the configuration of the container uniformly removed by the barreled part barreling finishing process according to claim 1, which is characterized in that: in the step S3, the initial position of the fixed blade in the container is unchanged, the distance between the wall of the container and the blade in different stages is changed, and discrete element simulation is carried out on the barrel polishing and finishing process of the blade parts.
3. The method for reversing the configuration of the container uniformly removed by the barreled part barreling finishing process according to claim 2, which is characterized in that: the single change in the distance of the vessel wall from the vane is the thickness of a monolayer of particles.
4. The method for reversing the configuration of the container uniformly removed by the barreled part barreling finishing process according to claim 2, which is characterized in that: at some stage of the blade processing, the container part structure changes inwards or outwards from the original configuration by an amount ofAt the time, by +.>As a numerical range of the normal force extracted in each data block of the blade surface, it is expressed as +.>Dividing into +.>Each interval, and count the frequency number in each intervalThe normal force distribution of the particle swarm acting on the surface of the blade in a certain period of time in each data block is obtained, and the normal force distribution is expressed as follows in a vector form:
in the method, in the process of the invention,the amount of change in the container part-structure to the inside or to the outside in comparison with the initial configuration is +.>Time->Vector expression of normal force distribution in each data block; />Is->The frequency of the normal force of the first interval within a data block, and so on.
5. The method for reversing the configuration of the container uniformly removed by the barreled part barreling finishing process according to claim 4, which is characterized in that:is the size of single particles; if the shape of the particles is spherical, the corresponding +.>Is the diameter of the spherical particles; if the shape of the particles is prismatic, the corresponding +.>The edge length of the prismatic particles; if the shape of the particles is conical, the corresponding/>Is the diameter of the bottom surface of the conical particles.
6. The method for reversing the configuration of the container uniformly removed by the barreled part barreling finishing process according to claim 4, which is characterized in that:
in step S4, when the rotary motion isStage, the number of partial configurations of the corresponding container is +.>When in use, the two parts are arranged and combined to coexist at +.>A combination in which y represents the y-th data block of all the data blocks MN; expression of permutation matrix>The method comprises the following steps:
wherein each behavior of the matrix is expressed by vectors under different local configurations of the container at the stage, and the first behavior is expressed by corresponding vectors under the initial configuration of the container;the amount of change in the container partial structure inwardly or outwardly as compared to the initial configuration, the change in the container partial structure inwardly being negative and the change in the container partial structure outwardly being positive; />Is the number of data blocks;
when constructing the blade surface uniformity evaluation model, all data blocks on the blade surface need to be constructedContrast vector of internal normal force vectorThe expression is as follows:
wherein n represents an nth data block among all the data blocks MN;
the expression of the blade surface uniformity evaluation model is:
in the method, in the process of the invention,to evaluate the difference coefficient of the blade surface uniformity, +.>For the difference of the modes>The angular difference for each vector;
wherein the difference of the modesThe expression of (2) is:
wherein n represents an nth data block among all the data blocks MN;
angular difference of each vectorThe expression of (2) is:
in the method, in the process of the invention,is the +.>Each interval;
by the difference coefficient of the uniformity of the surface of the bladeAnd calculating the optimal combination of the stage for the evaluation index to obtain the discrete point coordinates of the container boundary under the optimal combination.
7. The method for reversing the configuration of the container uniformly removed by the barreled part barreling finishing process according to claim 4, which is characterized in that: in the step S4, when the distribution uniformity of the normal force of the blade along the chord length direction is poor in the processing process of the blade and the container, the data blocks of the surface of the blade along the length direction of the blade body are integrated into a group, so that the uniformity of the surface of the blade in one direction is improved;
when the rotary motion isStage, the number of partial configurations of the corresponding container is +.>When the two are arranged and combined, the two are coexistentA combination in which y represents a y-th data block among the M groups of data blocks in the chord length direction; expression of permutation matrix>The method comprises the following steps:
the equivalent vector calculation formula for the single set of vectors is as follows:
wherein:the amount of change in the container part-structure to the inside or to the outside in comparison with the initial configuration is +.>When the blade surface is in the chord length direction +.>Equivalent vectors of the group vectors; />The number of data blocks along the length direction of the blade body;
the expression of the blade surface uniformity evaluation model is:
in the method, in the process of the invention,to evaluate the difference coefficient of the blade surface uniformity, +.>For the difference of the modes>The angular difference for each vector;
wherein the difference of the modesThe expression of (2) is:
wherein n represents an nth data block among the M groups of data blocks in the chord length direction;
angular difference of each vectorThe expression of (2) is:
in the method, in the process of the invention,is the +.>Each interval;
by the difference coefficient of the uniformity of the surface of the bladeAnd calculating the optimal combination of the stage for the evaluation index to obtain the discrete point coordinates of the container boundary under the optimal combination.
8. The method for reversing the configuration of the container uniformly removed by the barreling finishing process of the blade parts according to claim 6 or 7, wherein the method comprises the following steps of: when calculating the optimal combination of a certain stage, the combination matrix is arrangedEach row of the blade surface uniformity evaluation model is selected to form a vector set, and the vector set is substituted into an expression of the blade surface uniformity evaluation model to obtain corresponding +.>A value; finally selectingThe smallest group is used as the optimal permutation and combination; and taking the midpoint set of the container boundary corresponding to the obtained optimal combination as the discrete point coordinates of the container boundary at the stage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310807478.4A CN116522546B (en) | 2023-07-04 | 2023-07-04 | Container configuration reverse solving method for uniformly removing blade part through barreling finishing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310807478.4A CN116522546B (en) | 2023-07-04 | 2023-07-04 | Container configuration reverse solving method for uniformly removing blade part through barreling finishing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116522546A CN116522546A (en) | 2023-08-01 |
| CN116522546B true CN116522546B (en) | 2023-09-15 |
Family
ID=87390707
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310807478.4A Active CN116522546B (en) | 2023-07-04 | 2023-07-04 | Container configuration reverse solving method for uniformly removing blade part through barreling finishing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116522546B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109800512A (en) * | 2019-01-23 | 2019-05-24 | 东北大学 | Rotating cylindrical shell-variable cross-section disk-pretwist blade system dynamic modeling method |
| CN114117666A (en) * | 2021-11-16 | 2022-03-01 | 吉林大学 | Method for modeling blades of hydraulic torque converter |
| CN114738054A (en) * | 2022-05-20 | 2022-07-12 | 西北工业大学 | Design method of bionic turbine blade of aero-engine |
| CN115238419A (en) * | 2022-08-11 | 2022-10-25 | 陕西理工大学 | Axial flow compressor blade design method based on composite material |
| CN115455588A (en) * | 2022-08-29 | 2022-12-09 | 厦门大学 | Turbine blade precision casting mold surface reversible deformation design method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2012243B1 (en) * | 2007-07-05 | 2019-01-23 | Honda Research Institute Europe GmbH | Aerodynamic design optimization using knowledge extraction from analyzing unstructured surface meshes |
-
2023
- 2023-07-04 CN CN202310807478.4A patent/CN116522546B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109800512A (en) * | 2019-01-23 | 2019-05-24 | 东北大学 | Rotating cylindrical shell-variable cross-section disk-pretwist blade system dynamic modeling method |
| CN114117666A (en) * | 2021-11-16 | 2022-03-01 | 吉林大学 | Method for modeling blades of hydraulic torque converter |
| CN114738054A (en) * | 2022-05-20 | 2022-07-12 | 西北工业大学 | Design method of bionic turbine blade of aero-engine |
| CN115238419A (en) * | 2022-08-11 | 2022-10-25 | 陕西理工大学 | Axial flow compressor blade design method based on composite material |
| CN115455588A (en) * | 2022-08-29 | 2022-12-09 | 厦门大学 | Turbine blade precision casting mold surface reversible deformation design method |
Non-Patent Citations (1)
| Title |
|---|
| "NPU-LL叶片系列构型气动性能研究";赵清周 等;《机械科学与技术》;第41卷(第8期);1278-1288 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116522546A (en) | 2023-08-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101376229B (en) | Processing method and device for forming aspheric surface part by numerical control tangent line turning method | |
| CN116522546B (en) | Container configuration reverse solving method for uniformly removing blade part through barreling finishing | |
| CN103245306A (en) | Method for measuring centre line of cylinder body of rotary kiln in thermal state | |
| CN108747602A (en) | Utilize the method for circular arc array wheel grinding high order curve section cylinder array structure | |
| CN206825172U (en) | Wire rod mechanical derusting equipment | |
| US20060160472A1 (en) | Surface treated product, surface treatment method, and surface treatment apparatus | |
| Yang et al. | Effect of kinematic parameters considering workpiece rotation on surface quality in YAG double-sided planetary lapping with the trajectory method | |
| JP2002120116A (en) | Manufacturing method of outer tooth gear | |
| CN111950206A (en) | Design method of surface parabolic groove of miniature dynamic pressure gas thrust bearing | |
| PH12013502028B1 (en) | Abrasive medium for barrel polishing | |
| US20160184959A1 (en) | Airfoil masking tool and method of polishing an airfoil | |
| CN107097134A (en) | Wire rod mechanical derusting equipment | |
| JP2002126993A (en) | Manufacturing method for gear and its machining device | |
| CN103111928A (en) | Grinding method of numerical control coordinate of cam | |
| CN113059124A (en) | Preparation method of mold core of closed twisted blade | |
| CN208358459U (en) | Surface processing device is used in a kind of processing of tapping template | |
| CN102825534B (en) | The method of glass substrate for support fixture and manufacture magnetic recording medium | |
| Zhang et al. | The theoretical analysis and experimental study on the distribution characteristics of motion parameters in the process of honing gear | |
| Ahluwalia et al. | Experimental investigation of fixtured vibratory finishing | |
| CN209491621U (en) | A kind of sander for polishing through the pliers of sand casting forming | |
| CN115194572B (en) | Method for symmetrically grinding crankshaft journal | |
| Yushan et al. | Research on the mapping grinding of dimple surface with ordered pattern based on topological theory | |
| CN109562502A (en) | The preparation method and cup type grinding stone of grinding object | |
| CN107486430B (en) | Device for removing impurities in tooth sockets | |
| CN103506962A (en) | Novel impeller head capable of improving input shot quality |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |